thermo-elastic-plastic stresses technical … · kovacs^ considered the transient temperature...

fiS)'AJl RIA-82-U21

f^^ //'/o9 .^S-a I

TECHNICAL REPORT ARLCB-TR-81044

THERMO-ELASTIC-PLASTIC STRESSES

IN MULTI-LAYERED CYLINDERS

John D. Vasilakis

November 1981

TECHNICAL LIBRARY

us ARMY ARMAMENT RESEARCH AND DEVELOPMENT COMMAND LARGE CALIBER WEAPON SYSTEMS LABORATORY

BENET WEAPONS LABORATORY

WATERVLIET, N. Y. 12189

AMCMS No. 6111.01.91A0.0

DA Project No. 1T161101A91A

PRON No. 1A1281501A1A

APPROVED FOR PUBLIC RELEASE; DISTRIBUTION UNLIMITED

DISCLAIMER

The findings in this report are not to be construed as an official

Department of the A.rmy position unless so designated by other author-

ized documents.

The use of trade name(s) and/or mamifacture(8) does not consti-

tute an official indorsement or approval.

if...

' ■>-V-j.»''•?.

DISPOSITION

Destroy this report when it is no longer needed. Do not return it

to the originator.

^-7. ,^ i l f}^y': If.

-j ^,-i»^^-r-

SECURITY CLASSIFICATION OF THIS PAGE (Whan Data Bntarad)

REPORT DOCUMENTATION PAGE READ INSTRUCTIONS BEFORE COMPLETING FORM

1. REPORT NUMBER

ARLCB-TR-81044

2. GOVT ACCESSION NO. 3. RECIPIENT'S CATALOG NUMBER

4. TITLE (and SubUtla)

THEEMO-ELASTIC-PLASTIC STRESSES IN MULTI-LAYERED CYLINDERS

S. TYPE OF REPORT & PERIOD COVERED

6. PERFORMING ORG. REPORT NUMBER

7. AUTHORCaJ

John D. Vasilakis 8. CONTRACT OR GRANT NUMBERCs^

9. PERFORMING ORGANIZATION NAME AND ADDRESS

US Army Airmament Research & Development Command Benet Weapons Laboratory, DRDAR-LCB-TL Watervliet, NY 12189

to. PROGRAM ELEMENT, PROJECT, TASK AREA ft WORK UNIT NUMBERS

AMCMS No. 6111.01.91A0.0 DA Project No. 1T161101A91A PRON No. 1A1281501A1A

11. CONTROLLING OFFICE NAME AND ADDRESS

US Army Armament Research & Development Command Large Caliber Weapon Systems Laboratory Dover, NJ 07801

12. REPORT DATE

November 1981 13. NUMBER OF PAGES

24 14. MONITORING AGENCY NAME & ADDRESSfi/ dlltarant from Controllini OIHea) IS. SECURITY CLASS, (of Ma report)

UNCLASSIFIED

tSa. DECLASSIFICATION/DOWNGRADING SCHEDULE

16. DISTRIBUTION STATEMENT (ot thla Report)

Approved for public release; distribution unlimited.

17. DISTRIBUTION STATEMENT (of the abatrael entered In Btook 20, It dltierent from Report)

18. SUPPLEMENTARY NOTES

Presented at 27th Conference of Array Mathematicians, US Military Academy, West Point, NY, 10-12 June 1981. Published in proceedings of the conference.

19. KEY WORDS (Continue on reverae aide If neeeeaary and Identify by block number)

Thermo-Elastic-Plastic Response Multi-Layered Cylinders Thermal Loads Pressure Loads

20. ABSTRACT (Cimttaua an terermm (Mi tt it»c»aaaty aad. fderUity by block number)

One of the many efforts undertaken to increase the life of gun tubes and/or increase their resistance to erosion involves the use of liners fabricated from different materials. A finite difference computer code for investigating the thermo-elastic-plastic response of gun tubes has been expanded to include multi-layered cylinder response to time dependent boundary conditions. Considered are both cyclic heat input and cyclic stress input. Response

(CONT'D ON REVERSE)

DD FORM t JAM 73 1473 EDITtON OF f MOV 65 IS OBSOLETE

UNCLASSIFIED SECURITY CLASStFlCATIOM OF THIS PAGE (Wtmt Data Entered)

SECURITY CUASSIFICATION OF THIS PAGEQWian Dmtm Bntmnd)

20. ABSTRACT (Cont'd)

curves fron intjuta representative of repeated firing cycles are presented. The emphasis in this report is on the transient temperature response and on the thermo-elastic stresses and mechanical stresses in the layers.

SECURITY CUASSIFICATION OF THIS PAGEfWisn Data Entered)

TABLE OF CONTENTS Page

INTRODUCTION

DESCRIPTION OF THE PROBLEM

BOUNDARY CONDITIONS

RESULTS

CONCLUSIONS

REFERENCES

TABLES

I. MATERIAL PROPERTIES OF MULTI-LAYERED CYLINDER

LIST OF ILLUSTRATIONS

1. Typical Multi-layered Geometry.

2. Heating and Pressure Pulses.

3. Effect of Time Increment on Pulse Shape. Monobloc Tube,

4. Bore Temperature Change Under Repeated Firing. Monobloc Tube.

5. Bore Temperature vs. Time.

6. Bore Temperature vs. Time (5 Cycles).

7. Response of Monobloc Tube (Bore Stress) to a Given Stress Pulse.

8. Thermal Stresses Due to Single Firing Pulse. Monobloc Tube.

9. Bore Stress vs. Time. Elastic Response, Multi-layered Cylinder.

10. Bore Stress vs. Time Pressure Pulse.

II. Combined Thermal and Mechanical Loads.

12. Bore Stress vs. Time.

13. Bore Stress vs. Time.

1

2

6

8

18

23

12

4

7

10

11

13

14

15

16

17

19

20

21

22

•

INTRODUCTION

One of the many efforts undertaken to increase the life of gun tubes

and/or increase their erosion resistance involves the use of liners fabricated

from materials differing from the base material of the gun tube. Typical

properties sought in these materials, many of which are refractory materials

or alloys of them, are high melting points for protection against erosion due

to the high flame temperatures, different elastic moduli to effect trans-

mission of loads to the base gun tube, etc. Currently most designs are of the

two-layer system or liner-jacket type and with a variation that the liner may

be coated or not. This report does not consider coatings for reasons to be

mentioned later.

In this report, the response of monobloc and multi-layered large caliber

gun tubes due to a typical firing schedule is calculated. This response is

found using a finite difference computer code reported in references 1 and 2

for transient temperatures and thermo-elastic-plastic stresses. The program

was updated to accept time dependent boundary conditions and to apply to

multiple layers. A consistent set of data for a firing pulse was found in

reference 3 for a specific weapon and this configuration was chosen for this

study.

^Vasilakis, J. D., "Temperatures and Stresses Due to Quenching of Hollow Cylinders," Transactions of the Twenty-Fourth Conference of Army Mathematicians, ARO Report 79-1. ^Vasilakis, J. D. and Chen, P. C. T., "Thermo-Elastic-Plastic Stresses in Hollow Cylinders Due to Quenching," Transactions of the Twenty-Fifth Conference of Army Mathematicians, ARO Report 80-1.

^Kovacs, J. E., "Computer Methodology For Large Caliber Artillery Cannon Heating and Cooling," Technical Report ARSED-TR-80001, December 1980.

The computer program is a two part program. Knowing gas temperatures and

heat transfer coefficients as a function of time during the firing cycle

allows the computation of the transient temperatures in the gun tube. This is

accomplished in the first part of the program. These temperatures are then

used in the second part to calculate the associated thermc-elastic stresses.

The program is capable of computing the thermal response of the tube for any

desired firing cycle, thus monitoring an average temperature use at the bore.

This can be used in cook-off studies, cook-off being the undesirable condition

of premature propellant ignition. The temperatures at any time are saved on

disk and are used as input to the stress portion of the program. The interest

here is in the mechanical and thermal stresses due to the pressure pulse and

the thermal pulse respectively. It should be mentioned that the theinaal

problem and stress problem are treated as uncoupled.

DESCRIPTION OF THE PROBLEM

The partial differential equation for determining the temperature in a

cylinder is given by

19 3T 3T ■ (rkL(T) ~) = pL(T)cL(T) ~ (1) r 9r 3r 3t

where the superscript L refers to the layer number and

T is temperature,

k^(T) is thermal conductivity in layer L,

p^(T) is density in layer L,

c^T) is specific heat in layer L,

r is radial distance

and t is time. The problem is assumed to be axisymnetric and axial effects

are ignored. Figure 1 shows a typical geometry. At the interface between

layers, the following continuity conditions must apply:

continuity of temperature

■jL XL+1

^L

(2)

^L"

and continuity of heat flux

3T kL(T) —

3r

3T = k^+ld) —

3r (3)

where rL is the radius to the outer surface of the L^^ layer. Contact

resistance between layers is ignored at this time.

The above quantities are dimensionless, normalized to the properties of

the steel layer.* Thus if the thermal conductivity can be written as

kL(T) = kSLgokL(T) (4)

where k^(T) is the dimensioned thermal conductivity of the L*^^ layer and k^l-gQ

is the thermal conductivity of the steel layer at some reference temperature,

then for L = 1 kl(T)

feSL kHT)

So

and L > 1, kL(T) k^Q ■ = kL(T)

k^So k^So

(5)

(6)

*In the results that follow, one of the layers was steel. Other definitions or material properties can be used so long as one is consistent.

FIGURE 1. TYPICAL MULTI-UYERED GEOMETRY

The specific heat and density are defined in similar fashion. Also

r T r = - , T = (7)

° Tgas I

where Tg^s is initial gas temperature, and time

X = (8)

The stresses are computed in the second part of the program. Again,

finite differences are used. The equations of compatibility and equilibrium

are written at each node,

—- + - (oL - OLQ) = 0 (9) 3r r

3ee^ 1 -—- + - (eLg _ eL ) . Q (10) 3r r

where L identifies the layer. Between layers, the continuity conditions for

radial stress and radial displacement must be satisfied. Between the L and

L+1 layer, therefore, a\ = a^+lj. and u^ = u^+l (11)

Initial stresses may exist due to fabrication methods used for the multi-

layered cylinder. The Prandtl-Reuss equations are used to relate the incre-

mental stress and strain. The assvraiption of plane strain is used. The equa-

tions (9) and (10) are written in finite difference form. Expressions

relating incremental stress to incremental strain similar to those of Yamada,

et al* but including the effect of temperature are used to express equation

^Yamada, Y., Yoshimura, N., and Sakuri, T., "Plastic Stress-Strain Matrix and Its Application For the Solution of Elastic-Plastic Problems by the Finite Element," International Journal of Mechanical Sciences, 1968, V 10, pp. 343- 354.

(9) in terms of the incremental strains.

For the computation of the thermal stresses, the new temperature

distribution and temperature increments are used at each time step. As the

yield criterion is approached, the temperature increments are themselves

divided into smaller increments to maintain smaller load steps.

BOUNDARY CONDITIONS

It is important when solving for the response due to firing pulses of

these geometries to have a set of consistent boundary conditions. For the

thermal response, either the temperature versus time on the boundaries or the

gas temperature and heat transfer coefficients are required and for the pres-

sure pulse, the bore pressure versus time. Kovacs^ considered the transient

temperature response for several firing cycles, see Figure 2, and did give in

his report a complete set of data. The data is based on a program relying on

empirical information for heat flux and applied to a large caliber weapon with

chrome plating. It was felt that the heat transfer coefficients generated

would apply to a steel monobloc tube or to a multi-layered tube where the

steel layer was at the bore. Lacking better input, however, the data was used

in all cases.

Future plans include the incorporation of an initial program for the

purpose of analytically computing the heat transfer coefficients for the

designated multi-layer properties. The problems encountered in comparing

responses of different multi-layered designs would then be alleviated.


CO o LU CO

s CTJ

I-

CQ

Q -^ C«4

1^ -s

3 2 to

1." CO

-:

N~\

U 111

?:!

u>

g

Ui

13 «J^ X I—J

liJ Q: z> CO

s

RESULTS

Several runs have been made, mainly to show the different problems that

can be accommodated by the computer program. Once a geometry has been chosen,

either monobloc or multi-layer, and the material properties found, the first

part of the program can be run for temperature response versus time. One can

look at both the temperature distribution throughout the tube wall and the

change in bore temperature in time. If a firing cycle consists of a number of

firing pulses and pauses, the bore temperature can be monitored in time. If

stresses are required, the temperature distributions at each time step are

saved in a file which is subsequently used as input to the second part of the

computer program. These temperature distributions are used to compute the

thermal stresses. The associated stress pulse can also be applied to the

tube, either by itself for a mechanical response or with the thermal loads for

a combined response. As mentioned before, however, the thermo-mechanical

problem is considered to be uncoupled. If the distortion energy criterion is

satisfied, then an incremental thermo-elastic-plastic analysis will be per-

formed. It should be noted that while some examples showing elastic-plastic

response are presented, the loading generated from the data of reference 3 was

not of sufficient magnitude to cause this and the stress pulse was increased

to cause the program to perform a plasticity solution. If the problem is more

realistically modeled with material properties and yield strength a function

of temperature, it may not be necessary to artificially induce this type of

solution.


Figure 3 shows the result of the problem of thermal response due to the

heat pulse for a monobloc tube. The response to a single piilse is shown for

different time increments. An important function of this type of analysis is

to be able to predict bore temperatures under various firing cycles and for

long firing periods. Being able to use coarser time Increments allows the

prediction of bore temperatures for longer periods. Figure 4 shows the

response of a monobloc tube for about five cycles.

Table I shows the properties for the multi-layered geometry chosen. The

liner is a tantalum tungsten alloy (Ta-lOW) with a steel jacket. The bore

diameter is 3.351 inches, the outside diameter is 5.6 inches, and the

interface diameter is 4.1 inches. The properties are assumed constant in

temperature but a variation in temperature is allowed. Figures 5 and 6 are

equivalent to Figures 3 and 4 for a multi-layered tube. Figures 7 and 8 show

the stress response of a monobloc tube to a stress pulse and a thermal pulse,

respectively. It should be noted that most of these results show the effect

at the bore. During the early stages of the response, there is little effect

on the rest of the tube.

Figure 9 shows the stress response of a multi-layered cylinder (Ta-lOW/

Steel). The material behavior is assumed to be elastic. The change in the

tangential stress at the bore with time is shown for the stress pulse (M

curve) and for the temperature distributions (T curve). The combined curve

shows the computed stresses due to both the thermal and mechanical loading.

Since only elastic behavior occurs, however, the same combined loading curve

could be arrived at by assuming the results for the individual loads.

p

II

§ § ^ II II II

o I i o - I o - +

<c <a: o:

+ ■

S

• o

UD

LA

S 5 (SI X) 3yniViGdW3i

^

ffi

ff

C/5 LU (/> _J Z5

a_ .'-> ^ o

1—J

r«o X ^ s^ u ^ g

#1

1— z 1—1

^ 1—4

CM 1—

fe

13 UJ u. lib

r-i tr\ UJ

10

CVI

8 ui

CS. ^

a

S GL

8 ^

.11 rH UJ UJ

H= ?

UJ ce

LU

(j)XX) 3Hnivy3dW3i

11

1

B TH

fe 0 O

o « =«= CO ^^ ^^ C 3 » •H H H ^■.^

OQ CO =«fc

i-H 1—t .-1 ^-s o. a 0) u H a u ro e td m o '^ -a- Cti o p». <t \^ o o 00

o t-H CM a • « • 0)

■H 4J M <U cx o >o r~. •* M vO f-4 w-t

Oi • cn • CM • CM

V4 (U c

1-1 >J es <Ti

1—t cn r-» o CO o o o vO • • •

fed u Q.

CM fO O

vO r*. • • • ^H

43 O c w

o (0 fn ^H vO 3 • • •

•H en -* m T3 cd Oi

0 o rt (U

(U tu •o •T3 >-l •r4 •H (U CO la 4-1 U

S •s §

1

12

OJ

tfl > ai UJ 9 fV 1—

i Q cc

in 1—

UJ LU c/> n >- u3 ^

^*N.

~^ 1 ?^ Ul »- 1—1 oc _J 1 .Q = .<

CD

LA

1 ^ ^

Csi

O

CD CD

(^p<) 3ynivy3dW3X

13

.4c

^.^ ^ ^<^ ai

> UJ s II1 •-< A

1— jfj H- lU

fS to

5 tJJ ) Q: 3 CD

(rOTX) 3ynivy3dW3X

14

Ul

&

>

<

CO U. (A O LLl

to oo UJ cc: £

CO

LU

Q- co CO UJ

LU OC ZD CD

CD CD CVI o

c5

<D

15

LU

oo UJ a: => C3

CM CO <3

I

oq CD

I

16

0.50 —

0.25

0.0

Oe/O^pCM)

(M) MECHANICAL LOADING

(T) THERMAL LOADING

-0.25 —

-0.50 —

-0.75 —

.5 .8

TIME (xlO^)

HQ /O^P (COMBINED)

% /o;p(T)

1.0

FIGURE 9. BORE STRESS VS TIME,

ELASTIC RESPONSE^ MULTILAYERED CYLINDER

17

An elastic-plastic response due to the applied pressure pulse is shovm in

Figure 10. The curve labeled pressure is actually the radial stress at the

bore, Oj., and the pressure should be \a-^\. The other three curves are the

response of a monobloc steel tube and two multi-layered systems, a Ta-lOW

liner with a steel jacket and a steel liner with a Ta-lOW jacket. The figure

shows mainly the effect of the elastic modulus of the materials. The Ta-lOW

liner, having a modulus approximately one third less than steel, transmits the

load towards the interior of the tube better than the other configuration

which has a more rigid liner. Figure 11 was included just to show that the

stresses throughout the wall thickness are computed. The figure shows the

response of a Ta-lOW liner/steel jacket cylinder to combined thermo-mechanical

loads.

Figure 12 shows the elastic response due to thermo-mechanical loads in a

multi-layered cylinder with a steel liner and Ta-lOW jacket. Figure 13 shows

the thermo-elastic-plastic response for the same configuration. The radial

stress and the tangential stress at the bore are shown as the change in time.

CONCLUSIONS

The above results are an indication of the type of problems to which the

computer program can be applied. Several layers can be handled and for the

two-layer geometry, initial stresses due to interference fits (for fabrication

reasons) can be calculated. In either program part, the properties can be

considered as a function of temperature. While the program does not have the full

responsibility of a general purpose finite element program, for the allowed

geometry, a wide variety of behavior can be examined.

18

-—^-f^,:i-ft,A.f ■

FiGURElO. BORE STRESS VS TIME

PRESSURE PULSE

ELflSTIC/PLflSTIC

PRESSURE ..Z

TR-ION/STEEL

STEEL ..X

STEEL/Tfi-ION

0.50

Y

19

0.1 —

0.0

o;/o^p

-0.1 .__

RADIUS

1.0

-0.2

-0.3

-0,4

FIGURE 11. COI^INED THERMAL AND MECHANICAL LOADS

(MULTI-LAYERED CYLINDER, STRESS

DISTRIBUTION THROUGHOUT THE WALL

FOR A SPECIFIC TIME)

-0.5

20

0.50

FIGURE 12. BORE STRESS VS TIME. ELASTIC RESPONSE.

COMBINED THERMAL AND MECHANICAL LOADS

MULTI-LAYERED CYLINDER. STEEI/TA-ICW

21

0.75

x\ 0.50

/

\ (COMBINED RESPONSE)

0.25 \

STRESS TIME (xlO^)

0.0 \ .2 A \ , ^^ 1 ^ 1.0

\ V \ y^'^^^t /Oyp

-0.25 \

-0.50

-0.75 -^

_i m I -T^iinc 1"? \ ir>DC QxDcee \i e TTMC

ELASTIC-PLASTIC RESPONSE. STEEL/TA-1CW.

COMBINED THERMAL AND MECHANICAL LOADS,

22

REFERENCES

1. Vasilakis, J. D., "Temperatures and Stresses Due to Quenching of Hollow

Cylinders," Transactions of the Twenty-Fourth Conference of Army

Mathematicians, ARO Report 79-1.

2. Vasilakis, J. D. and Chen, P. C. T., "Thermo-Elastic-Plastic Stresses in

Hollow Cylinders Due To Quenching," Transactions of the Twenty-Fifth

Conference of Army Mathematicians, ARO Report 80-1.

3. Kovacs, J. E., "Computer Methodology For Large Caliber Artillery Cannon

Heating and Cooling," Technical Report ARSED-TR-80001, December 1980.

4. Yamada, Y., Yoshimura, N., and Sakuri, T., "Plastic Stress-Strain Matrix

and Its Application For the Solution of Elastic-Plastic Problems by the

Finite Element," International Journal of Mechanical Sciences, 1968, V 10,

pp. 343-354.

23

TECHNICAL REPORT INTERNAL DISTRIBUTION LIST

NO. OF

CaMANDER

■ CHIEF, DF/ELOB.IMT ENGINEERING BFJUMCH ATTN: DEmR-LGB-DA

-DM -DP -DR -DS -DC

CHIEF, ENGINEERING SUPPORT BRANCH ATTN: DPcDAR-LCB-SE

-SA

CHIEF, RESEARCH BRANCH ATTN: DRDAR-LCB-RA

-EG -m -RP

CHIEF, LWC MORTAR SYS. OFC. ATTN: DPDAR-LCM

CHIEF, IMP. 8lfM MORTAR OFC. ATTN: DHDAR-LC3-I

TECHNICAL LIBRAE! ATTN: DRDAR-LCB-TL

TECmiCAL PUBLICATIONS & EDITING UNIT ATTN: DRDAR-LCB-TL

DIRECTOR, OPERATIONS DIRECTOPATE

DIRECTOR, PROCUREMENT DIPJICTOPATE

DIRECTOR, PRODUCE ASSURANCE DIRECTORATE

1 1 X 1 1 1 1

1 1 1

2 1 1 1 1

1 1

1 1

1

1

1

NOTE; PLEASE NOTIFr ASSCC. DIRECTOR, BENET 'AmPONS LABORATORI, ATTN; DRDAR-LCB-TL, OF AhVI REQUIPuED CHANGES.

TECHNICAL REPORT EXTERNAL DISTRIBUTION LIST

NO. OF COPIES

NO. Ol' copii:s

ASST SEC OF THE ARMY RESEARCH & DEVELOPMENT ATTN: DEP FOR SCI {, TECH THE PENTAGON WASHINGTON, D.C. 20315

COMMANDER US ARMY TANK-AUTMV R^D COMD ATTN: TECH LIB - DRDTA-UL

MAT LAB - DRDTA-RK WARF^EN, MICHIGAN 48090

COMMANDER US ARMY MAT DEV 5 READ. COMD ATTN: DRCDE 5001 EISENHOWER AVE ALEXANDRIA, VA 22333

COMMANDER US ARMY ARRADCOM ATTN: DRDAR-LC

-LCA [PLASTICS TECH EVAL CEN)

-LCE -LCM -LCS -LCW -TSS (STINFO)

DOVER, NJ 07801

COMMANDER US ARMY ARRCOM ATTN: DRSAR-LEP-L ROCK ISLAND ARSENAL ROCK ISLAND, IL 61299

DIRECTOR US ARMY BALLISTIC RESEARCH LABORATORY ATTN: ■ DRDAR-TSB-S (STINFO) ABERDEEN PROVING GROUND, MD 21005

COMMANDER US ARMY ELECTRONICS COMD ATTN: TECH LIB FT MONMOUTH, NJ 07703

COMMANDER " US ARMY MOBILITY EQUIP R^D COMD ATTN: TECH LIB FT BELVOIR, VA 22060

a 1

1 1 1 1 2

COMMANDER US MILITARY ACADEMY ATTN: CHMN, MECH ENGR DEPT WEST POINT, NY 10996

US ARMY MISSILE COMD REDSTONE SCIENTIFIC INFO CEN ATTN: DOCUMENTS SECT, BLDG 4484 REDSTONE ARSENAL, AL 35898

COMMANDER REDSTONE ARSENAL ATTN: DRSMI-RRS

-RSM ALABAMA 35809

COMMANDER ROCK ISLAND ARSENAL ATTN: SARRI-ENM (MAT SCI DIV) ROCK ISLAND, IL 61202

COMMANDER HQ, US ARMY AVN SCH ATTN: OFC OF THE LIBRARIAN FT RUCKER, ALABAMA 36362

COMMANDER US ARMY FGN SCIENCE 5 TECH CEN ATTN: DRXST-SD 220 7TH STREET, N.E. CHARLOTTESVILLE, VA 22901

COMMANDER US ARMY MATERIALS § MECHANICS

RESEARCH CENTER ATTN: TECH LIB - DRXMR-PL WATERTOWN, MASS 02172

NOTE: PLEASE NOTIFY COMMANDER, ARRADCOM, ATTN: BENET WEAPONS LABORATORY, DRDAR-LCB-TL, WATERVLIET ARSENAL, WATERVLIET, N.Y. 12189, OF ANY REQUIRED CHANGES.

TECHNICAL REPORT EXTERNAL DISTRIBUTION LIST (CONT.)

crmiANDER us ARMY RJ'2L;RCH OFFICE. P.O. BCK 12:. 11 RESEARCH TRUiNGLE PARK, NC 27709

Cax^'ANDER US ARMY HARi^ DTAJJiOND JAB ATTN: TECH LIB 2800 Pa^ER MILL ROAD ADELPHIA, ML 20783 .v

NO. OF NO. OF COPTfiS

CCMMANDER DEFENSE TECHNICAL INFO CE1>ITER

cnPTi'S

1 ATTN: DTU-TCA CAMERON STATION ALEXANDRU, VA 223U

12

METAI5 4 CERAMICS INFO CEN BATTELLE COLUMBUS LAB 505 KING AVE COLUMRIIS CHTO ^1201

DIRECTOR US ARMY INDUSTRIAL BASE KNG ACT ATTN: DRXPZ-I^ ROCK ISLAND, IL 61201

CHIEF, r/ATERLALS BRANCH US ARfvIY R/o3 GROUP,, EUR BOX 65, FPO S.Y. 09510

Ca^MVNDER '' • MAVAL SURFACE WEAPONS CEN ATTN: CHIEF, MAT SCIENCE DIV DAHIJ3REN, VA. 22448

DIRECTOR US NAVAL RESEARCH LAB ATTN: DIR, IffiCH DIV

CCTE 26-27 (DOC LIB) WASHINGTCN, D. C. 2037f

NASA SCIENTLFIC & TECH INFO FAC. P. 0. BCK 3757, ATTN: ACQ. BR BALTmORE/W.SHINGTCN INTL AIRPORT MARYLAND 21240

i 1

MECHANICAL PROPERTIES DATA CTR BATTELLE COLUMBUS UB 505 KING AVE COLUMBUS. OHIO 43201

MATERIEL SYSTB^ ANALYSIS ACTV ATTN: DRXSY-MP ABERDEEN PROVING GROUND MARYLAND 21005

NOTE: PLEASZ NOTIjFY CCWMANDER, ARRADCCW, ATTN: BENET WEAPONS UBORATORY, DRTAF.-LCB-TL, WATERVLIET ARSENAL, WATERVLIET, N.Y. 12189, OF ANY REQUIRED CHANGES.

thermo-elastic-plastic stresses technical … · kovacs^ considered the transient temperature...

Documents